Number: Date : Revision 

### 2 · ATA System : 

### 727-52.0142 July 26, 1990 

### April15, 1993 5234 

### Comme rcial Airp l ane G roup 

# 727 Service Bulletin Revi s i o n Tran s mittal Sheet

SUBJECT: DOORS- MAIN CARGO DOOR- LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR H I NGE FITTI N G R EPLACE MENT This revision includes all pages o r the service bulletin . CO M PLIAN CE INFOR MA TIO N R ELATED TO T HI S REVISIO N Federal Aviation Administration (FAA) Alrwonh l ness DlrectJVe 91-22-()4 , Amendment 39-8064 , is rela ted to thiS service bulletin . No more wor1< Is necessary on a1rplanes changed by the lmtial release 

### or Revision 

### 1 of t his service bulletin . SU MM ARY This revision adds instructions to t rim the hinge filling If t here is interference between t he cam and the hinge filling when th e door is in the closed posltlon . Optional fasteners are added for the Insta ll ation of the hinge fitting . This revision also defines the maximum all owable wear limits for the latch cams. Circle note 

### 10 of F i gure 

### 3 Is revised. Paragraph I.A.. Effect ivity, shows changes of a irpl ane operators . Each opera tor shou l d examine the Effectivity paragraph for changes . Vertical lines are put on the left edge of each page , e xcept In Paragraph lA. Effectlv•ty, to show the location of Important changes. Pages With a revision number and date, but no verllcal lines have 

### no Important changes REVISION HISTORY lnllial Release : Revision 

### 1 Revisi on 2 · July 26, 1990 June 

### 4 , 1992 April15 , 1993

BOE INC COMM E R Cllll. AIRPlANE GROU P P 0 BOX3701 SI:ATTLE. W ASH INGTON 96 124•2207

# ,

## BDIIND

N umber: Date Revision 2: AT A System: 727-5. 2-0142 July 26, 1990 April15. 1993 5234 

### Commercia l Airplane Group 

# 727 Service Bullet in S umm a ry

SUBJECT: DOORS· MAIN CARGO DOOR· LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR H INGE FITIING REPLACEMENT BAC K GROU N D The main cargo doors on the 727 Cargo and Freighter airplanes are almost lhe same as those on the 757 Package Freighter airplane. When the 757 Package Freighter was designed, better latch cams and better hinge fittings for the pressure relief doors were designed for the main cargo 

### door. Boemg has received several reports of wear of the lock stop part of hinge fittings on the pressure relief doors on 707 and 727 Cargo and Freighter airpl anes. Boeing has also received reports of wear o f l he latch cams on the main cargo doors on 707 and 727 Ca rg o and Freighter airplanes. Wear of th e l ock stop part o f the hinge fitUngs and of lh e latch cams is thought to be caused by Incorrect operallon sequence of the hydraulic system of the main cargo door. This service bulletin shows how to Install the better latch cams and hinge fittings on main cargo doors. lnslallalion of the better parts Will extend the service life of 

### the door latch system. Contmued operation with installed latch cams and hinge fillings that are wom beyond the lim11s g1ven 1n this servoce bulletm is not satisfactory Persons cannot make sure that the main cargo door Is correctly latched and locked under all possible operallona l conditions i f the hinge fitllngs or the latch cams a re worn beyond the limi t s given In this service bullelln. ACTI ON At the next 

## •c• check after receipt of this service bulletin, not to exceed 3000 night-cycles, do a v1sual Inspection of the mating surfaces on the hinge fil1ings and the latch cams. 

### If the hinge fillings are not 

## worn, or ere 

### worn Within the limits given tn this service bulletin. either lnslall 

### new h1nge fil1ings and latch cams, or do 

### the visual Inspection agam at each ·5c· check, or 8000 fligh t-hours, w hichever occurs sooner. 

### If 

### the hinge fittings are wom beyond the limits given In this service bulletin , Install new hinge fittings and l atch cams. If lhe latch cams ere worn or da maged , Install new hinge fittlngs and latch cams. Return to the normal inspeclion I nterval a fter the new h inge fittings and latch cams are Installed as shown In this service bulle6n . Federal Aviation Administration {FAA) Airworthiness Directive 91-22-04. Amendment 39-8064, is related to this service bulletin. EFFECTIVI TY AII727 - 100C and 727-200F senes airplanes MANPOWER Total Man-hours • 34 for each airplane Elapsed Time· 17 Hours M ATERIAL INFORMATION Boeing Supplied Kll Refer to Paragraph I.F • Mat8rlal • Pnce and Availability.

80£1 NO

**COM~ERCIAL** AIRPlANE GROUP P 0

**eo~** 3707 SEATTLE. WI\SHINGTON 98124-2207 Summary Page 1 of 2

### B OEI N G SE RVIC E BU L LE T I N 727-52-0 1 42



# &:? FIIO

# ~lNBO

- PRESSURE REll EF DOOR 

# rsy...__ 0 / REPLACE

# TH~ ON EACH PRES HINGE FlTTlNGS (2 PLACES) SURE RELIEF DOOR

Jul26190 REV 2 · Ap 

### .. r15193 

# &:? F\10

# ~l NBD REPLACE CAMS

# ANDT~~ LATCH (4 PLACES) E BELLCRANK

Summary 

### p

### age 2 

### or 2

## BDII.IVII

Number : 727-52..()142 Date: July 26. 1990 Revision 2 : April15 , 1993 ATA System : 5234 

### Commercial Airplane G roup 

# 727 Service Bulletin

SUBJECT: DOORS- MAIN CARGO DOOR- LATCH CAM REPLACEMENT AND PRESSURE RELIEF DOOR HINGE FITTING REPLACEMENT I . PLANNING INFORMATION A . Effe ctivity 1. Airplanes Refer to Service Bullelln I ndex Document D6-9825, Part 3 for Airplane Variable Number, Une Number, and Serial Number data . This service bulletin is for only these airplanes : IDENTIFICATION BY CUSTOMER. CUSTOMER CODE. GROUP AND VARIABLE NUMBER AERO PERU (PER) E5278 ALASKA AIRLINES (ASA) E5058 E5142 AMERICAN I NTERNATIONAL AIRWAYS, INC. (CKF) E5050 AMERIJET IN TERNATIONAL. INC. (AMJ ) E5161 E5403 ARIANA AFGAN AIRLINES CO., LTD (AFG) E5410 E5424 AVIANCA (AVI) E5451 E5453 BELGIAN AIR FORCE (BLG) E5351-E5352 BRADLEY A I R SERVICES (BRS) E5112 E5141 E5482 CHINESE AIR FORCE (CAF) E5409 E5435 CONTINENTAL AIRLINES. INC . (CAL) E5201

Jul26190 REV. 2 : Apr 15193 727-52-0142 Page 1 of 33

### CORSAIR (CRA) E5114 

### BOEING SERVICE BULLETIN 727-52-0142

D H L CORPORATION/WORLDWIDE COURIER EXP. (DHL) E5046-E5047 E5273-E5274 E5281 E5382 E5402 D IGEX AERO CARGO (DGX) E5481 DOMINICANA A I RLINES (DOM) E5404 ECHO BAY MINES (EKO) E5418 EVERGREEN INTER NATIONAL A I RLINES (EVR) E 5104·E5105 E5108 E5277 E5426 FAMCO AVIATION AND MARITIME SERVICES LTD ( FAM ) E5353 FEDERAL AVIATION ADMINISTRATION (FAA) E5241 FEDERAL EXPRESS (FED) E5048-E5049 E5052·E5054 E5056-E5057 E5059·E5063 E5067 E5163-E5164 E5221-E5224 E5226-E5240 E5242 E5408 E5454 QL501-QL515 ITAPEMIRIM TRANSPORTES AEREOS S.A. ( I TP) E5406 KELOWNA FLIGHTCRAFT AIR CHARTER L TO . (KEL) E5001 E5428 LLOYD AERO BOLIVIANO (LAB) E5421 NATIONAL AIRLINES LTD (NAN) E5501 NOMADS . INC . (NOM) E5279 REEVE ALEUTIAN AIRWAYS. INC. (RW) E5035 E5040 ROYAL NEPAL AIRLINES (RNA) E5419 ROYAL NEW ZEALAND A I R FORCE (RNZ) E5065 E5068 RYAN INTERNATIONAL AIRLINES (RYN) E5101-E5102 ES420

E5003 E5007-E5011 E5031-E5032 E5039 E541 1 E5413 E5415 E5433 E5041-ES042 ES381 E5483 E5502

Jul26/90 REV 2 : Apr 15/93 727-52-0142 

### 2

### BOEI N G SERVICE B U L LETIN 727-52-0 1 42
TAESA (TES) E5455 UNITED PARCEL SERVICE (UPS) E5002 E5004-E5006 E5033-E5034 E5051 E5106- E5107 E5109-E5111 E5225 E5243-E5245 E5251-E5252 E5301-E5306 E540 1 E5405 E5429 VARIG AIRLINES (VAR) E5272 E5407 E5412 IDEN TIFICATION 

### BY VARIABLE NUMBER E5001-E5011 E5031-E5068 E5101-E5116 E5221-E5245 E5251-E5252 E5271-E5281 E5401 -E5424 E5426-E5429 E5433 E5501-E5502 QL501·QL515 

### 2. Spares E5036 E5113 E5271 E5417

E5141-E5143 E5301 -E5306 E5435 E5038 E5115-E5116 E5275-E5276 E5422-E5423

E5161-E5164 E5351-E5353 E5451 · E5455 E5043-E5045 E5162 E5280 E5427

E5201-E5203 E5381-E5382 E5481-E5483
Examine your spares supply for the parts identified in Paragraph II.D. , Existing Parts Accountability. If any parts are found, refer to Paragraph II . D., Existing Parts Accountability, for the recommended use .

Jul26/90 REV. 2: Apr 15/93 727-52-0142 

### 3

### BOEING SERVICE BULLETIN 727-52-0 142

B. Reason The main cargo doors on the 

### 727 Cargo and Freighter airplanes are almost the same as those on the 

### 757 Package Freighter airplane . When the 

### 757 Package Freighter was designed , better latch cams , and better hinge fitllngs for the pressure relief doors were designed for the main cargo door. The new latch cams and hinge fiUings for the 

### 757 Package Freighter were designed to provide better resistance to wear. This service bulletin shows how to install the better latch cams and hinge fiUings on the main cargo doors on 727 Cargo and Freighter airplanes. I nstall ation o f the better parts on the main cargo doors will e xtend the service life of the door latch system. Boeing has received severa l reports of wear of the lOCk stop part of hinge fitUngs on the pressure relief doors on 707 and 727 Cargo and Fre ighter airplanes. Boeing has a l so received reports ofwear of the latch cams on the main cargo doors on 

### 707 and 

### 727 Cargo and Freighter airplanes. Wear of the lock stop part of the hinge fittings and of the latch cams Is thought to be caused by Incorrect operation sequence of the hydraulic system of the main cargo door. Incorrect operation sequence of the hydraulic system of the main cargo door can occur In service due to wear of components of the door's hyd raulic system, or due to a hydraulic system that is not adjusted correctly. Continued operation with Installed latch cams and hinge fittings that are wom beyond the limits given In this service bulletin Is not satisfactory. Persons cannot make sure that the main cargo door Is correctly locked and latched under all possible operational condillons if the hinge frttings or the latch cams are wom beyond the limits given In this servi ce bulletin. Revision 

### 1 was Issued to include a new top kil that supersedes the old top kit. The new kit Includes two latch cams and a bellcrank for each station . The latch cams and bellcrank come as a matched set with holes drilled in line through the mating parts . This revision also adds instructions to trim the shear web at the forward and 

### all l atch cams . New Instructions on how to locate the pressure door hinge fittings are added . Revision 

### 2 adds Instructions to trim the hinge fitting If there Is interference between the cam and the hinge fitting when the door is In the closed position . Optional fasteners are added for the installation of the hinge fitting . This revision also defines the maximum allowabl e wear limits for lhe latch cams. Circle note 

### 10 or Figure 

### 3 is revised.

Jul26/90 

### REV . 2 : Apr 15/93 

### 727-52-0142 

### 4

### B O E I NG S ER V I CE BUL L ETIN 727- 52..() 142

C. Description At 

### lhe next 

# ·c· check after receipt of this service bullebn, not to exceed 

### 3000 ftoght-cyctes, do a visual Inspection or the mating surfaces of the hinge filtlngs (on the pressure relief 

### doors) and the latch cams. lr the hinge filtlngs are not worn, Of are worn within the limits given in this service bulletin. either Install the new hinge fittings and latch cams as shown in this service bulletin, or do the v isua l Inspection again at each 'SC' check. or 8000 night-hours. whichever occurs sooner . 

## tr the hinge finfngs are worn beyond the limfls given in this service bullelln , Install the new h i nge finings and latch cams as shown in this service bulle tin. 

## rr the latch cams are worn or damaged, Install the new hinge fillings and latch cams as shown In this service bu ll elln. Arter the new hinge fillings and l atch cams are insta ll ed. re turn to the norma l Inspection Interval . lr It Is necessary to Install the new hinge fillings and latch cams. remove the lining and the insulation from the lower part of the main cargo door. Remove and discard the four pairs of latch cams along with their matched bellcranks . Install new latch cams and their matched bellcranks on the main cargo door, along with new latched-and-locked Indicators Remove the honge fittings from the pressure relief doors on the main cargo 

### doOf and Install new hinge fittings on 

### lhe pressure relief doors. Do a lest of the main cargo 

### doOf to make sure lhatlhe door operetes. latches. and locks correctly. Do a lest of the control system for 

### lhe door to make sure 

### il operates correctly. 

### Do a test of the wamong system for the main cargo dOOf to make sure it operates correcUy Install the lining and the insulation on 

### lhe Inside of the cargo door and return the airplane to service Federal Aviation Adm inistration (FAA) Airworthiness Directive 

### 91-22·04, Amendment 

### 39-8064, Is related lo this service bulletin. NOTES :1. If the main cargo door was deactivated as shown In Service Bulletin 727-29-0053 "Main Cargo Door Deacllvallon/Reacllvallon System I nstallation". and no allempt has been made to open the cargo door after it was deactivated, then the Inspection shown in this service bulletin can 

### be Ignored 

### 2. If the main cargo door was deactivated as shown In Service Bulleton 727-29..0053 "Main Cargo Door Deactlvation/ReacttVatoon System Installation" then 

### lhe changes shown In this service bulletin can be Ignored 

### 3. Time wtll 

### be saved i f the changes shown In this service bulletin are done at the same bme as the changes shown In Servoce Bulleton 727-52A0124 "Main Cargo 

### Door Cam Support Fitting Inspection and Replacement• D. App r oval This service bulletin was examined by the Federa l Aviation Adm inistration (FAA). The repairs and changes specified In this service bulletin comply with the applicable Federal Aviation Regulations (FAR) and are FAA approved The FAA has examined the lnspecllon and replacement procedures specified In Revision 

### 2 to Service Bulletin 727-52-()142, "DOORS - MAIN CARGO DOOR - LATCH CAM REPLACEMENT AND PRESSURE REUEF DOOR HINGE FITIING REPLACEMENT" . The FAA has approved the Inspection and replacement procedures on Revisoon 2 of Service Bullebn 727-52·0142 as an allemallve to those specofaed in Airworthiness Dorecttve (AD) 

### 91-22-04 Amendmenl39-a064

Jul26/90 REV 2: Apr 15193 727-52-0142 5

### BOEING SERVICE BULLETIN 72 7 -52-0142

E. M anpower Approximately 34 man-hours are necessary to do this change on one airplane • The data bel ow shows an estimate of the man-hOurs necessary lo do this change for each airplane . This estima te is for d ir ect labo r only, done by an experienced c rew . Adjust lhe estimate with operator man·hour data If necessary . The estima te does not i ncl ude lost time . These are some examp l es or lost time: Time to adjust to t he workplace, Time to sched u l e the work, Time to examine the work, Tl m e to cu re the materia l s. Time to make the parts, Ti m e l o find the tool s N u mber of Elapsed Task Persons Man-H ours Time (Hours) Open Access 

### 2 2 1 Change 

### 2 26 13 C l ose Access 

### 2 2 1 Test 

### 2 4 2 TOTAL FOR AIRPLANE 34 

### 17 F . Mat e r i al - P rice and Av ail ability Boeing can supply the kit shown in Paragraph I I.A., Parts Necessary For Each Airpl ane, as shown be l ow. Kit availability is shown in lhe Reorder Lead Time (ROLT ). ROL T is calculated from the date Boeing gets lhe pu rchase o rder. Kit Numbe r 65-93535-1 (a) 65- 93535-9 Name Top Kit Top K i t ROLT (weeks) 

### 51 Unit Price thru Oct 

### 3, 1993 $ 

### 1 5,326.00 (a) Top Kit 65-93535- 1 Is held f rom more sales . Top Ki t 65-93535-9 supersedes o l d Top Kit. The kits are subject to the tenns and conditions or Boeing's standard purchase order acknowl edgment. After the Unit Price date. new price and ROL T data Is applicable. Prices are in United States Dollars. Terms : Net 

### 30 days . Send purchase orders and letters about the supply data to the Director of Spares and refer to this service bulletin number. 

### G . Special Tools ·Price and Availability None H. W e igh t and B al ance None

Jul26 /90 REV . 2 . Apr 15193 

### 727-52-0142 6

### BOEING SE RV I CE BUL LETI N 727-52-0142

I. References 1 . Existing Data: a. 727 Maintenance Manual Subjects 52-11-0,52-34-0,52-34-11,52-34-161,52-34-171,52-70-00, 52-70-01 b. Overhaul Manual 52-36-61, 52-36-62 c. 727 Structural Repair Manual Chapter 51 d. Boeing Service BulleHns : o 727-29-0053 "Main Cargo Door Deactivation/Reactivation System Install ation• o 727-52A0124 "Ma in Cargo Door Cam Support Fitting I nspection and Replacement• e. Boeing Service Letters : o 727-SL-52-4 "Main Cargo Door Pressure Door Locking Stops" o 727-SL-52- 19 • Main Cargo Door Partial Opening In Flight" 

# r. FAA Airworthiness Directive 91-22-04, Amendment39-8064 2. Data supplied with th is service bulletin: None 

### J. Publications Changed Publication Overhaul Manual 727 Illustrated Parts Catalog 

### K

. Electrical Load Data

Not changed

Jul26/90 REV . 2 : Apr 15/93 Chapter-Section 52-36 52-30

727-52-0142 

### 7

### BOEING SERVICE BULLETIN 

### 727-52-0142

II. MA TERI A L INFORMATION A. Parts N ecessary For E ach Airplane 1 . To get \he kit shown below, refer to Paragraph I. F., Material- Price and Availability. NOTE: Top kit is divided Into subkits to make Installation of the parts easier. One 65-93535-9 top kit and operator supplied materials specified In Paragraph II.A .2.. Parts and Materials Supplied by the Operator, are necessary to change each airplane. 65-93535- KIT· MAIN CARGO DOOR LATCH CAMS AND LOCK FITTI NGS

-6 -5 -4 -3 -2 -1 Quantily Part Number Nomenclature 65-93535-1 Top Kil (a) 1 65-93535-2 Kit, Latch Cams and Be ll crank I nstallation, Body Station 495 65-93535-3 Kit, Latch Cams and Bellcrank I nstallation, Body Station 530 65-93535-4 Kit. Latch Cams and Be ll crank I nstallation, Body Station 570 65-93535-5 Kit, Latch Cams and Bellcrank I nstallation, Body Station 610 2 65-93535-6 Kit, Pressure Relief Valve Hinge I nstallation. Body Stations 510 and 590 143N6027-1 Cam 1 143N6027-2 Cam 1 143N8060-1 Cam 1 143N8060-2 Cam 1 65-93535-7 Hinge Fitting 

### 1 65-93535-8 Hinge Fitting 

### 1 1 69-2 1 969-11 Bellcrank 1 69-21969-12 Bellcrank 

### 1 69-23438- 1 Cam 69-23438-2 Cam 1 69-23439-3 Cam 1 69-23439-4 Cam 1 1 69-34974-3 Bracket. Lock I ndicator 1 69-34974-4 Bracket Lock Indicator 1 1 AN960C616L Washer 2 2 2 2 AN960PD8L Washer 1 1 BACB30EL5CN19 Boll , Countersink 3 6 6 3 BACW10P208S Washer

Jul26/90 REV. 2 : Apr 15193 727-52-0142 

### 8

### BOE I NG SERVICE BULLE TI N 727-52-0142

65-93535- KIT- MAI N CARGO DOOR LATCH CAMS AND LOCK FITTINGS



### -6 ·5 

### -4 ·3 ·2 

### ·1 Quantity Part Number Nomenclature 10 M S20470B8-14 Rivet 3 6 6 3 NAS11 04 -20W Bolt 1 1 NAS1105-20W Bolt 1 1 1 

### 1 NAS602-7 Screw 

### 1 1 

### 1 NAS679A08W Nut 3 6 6 3 NAS679A4W N ut 2 2 NAS679A5 Nul (a) Top Klt 65-93535·1 Is held from more sales. Top Kl l65·93535·9 replaces o ld top kit. 65-93535- K IT· MAIN CARGO DOOR LATCH CAMS AND LOCK F ITTING S

-6 -13 - 1 2 -11 ·10 ·9 Quantity Part Number Nomenclature 65-93535·9 Top Kit 1 65·93535- 1 0 Kit , Latch Cams and Bellc rank Install ati on, Body Station 495 1 65-93535-11 Kit, La tch Cams a nd Bellcrank Insta ll ation, Body Station 530 1 65-93535- 1 2 Kit, Latch Cams a nd Bellcrank Installation , Body Sta tion 570 1 65-93535-13 Kit , Latch Cams and Bellcrank Installation . Body Station 610 2 65·93535-6 Kit , Pressure Relief Valve Hinge Installat ion, Body Stations 510 and 590 1 65-93535-20 Cam 1 65-93535-17 Cam 1 65-93535-14 Cam 1 65-93535-22 Cam 1 65- 93535-7 Hinge Rttlng 65-93535-8 H inge FiHing 1 1 65·93535-18 Bellcrank 1 

### 1 65-93535-15 Bellcrank 1 65-93535-23 Cam 1 65-93535-16 Cam 1 65-93535-19 Cam

Jul 26/90 REV. 2 : Apr 15/93 727·52-0142 

### 9

### BOEING SERVICE BULLETIN 

## 727-52-0142

65-93535- KIT- MAIN CARGO DOOR LATCH CAMS AND LOCK FITTINGS

-6 -13 -12 -11 ·10 -9 Quantity Part Number Nomenclature 1 65-93535-21 Cam 1 1 69-34974-3 Bracket, Lock Indicator 1 69-34974-4 Bracket, Lock Indicator 1 1 AN960C616L Washer 

### 2 2 2 2 AN960PD8L Washer 1 1 BACB30EL5CN 19 Bolt , Countersink 3 6 

### 6 3 BACW10P208S Washer 1 0 MS20470B8-14 Rivet 3 6 6 3 NAS1104-20W Bolt 1 1 NAS11 05-20W Bon 1 1 1 NAS60 2-7 Screw 1 1 1 1 NAS679A08W Nut 3 6 6 3 NAS679A4W Nut 2 2 NAS679A5 Nut 2 . Parts and Materials Supplied by the Operator: NOTE : Refer to 727 StnJctural Repair Manual Chapter 51 for alternative fasteners. Quantity 50 5 7 2 16 20 20 14 16 As Necessary 

### As Necessary 

### As Necessary 2

Jul26/90 REV . 2 : Apr 15193 Part Number or Specification MS20470D6·7 BACB30FP6-3 BACB30FP6-4 BACB30FP6-5 BACB30FP8A( ) BACB30GYBA( )X BACC30K8 BACC30M6 BACC30M8 BMS 10-11. Type 

### I BMS 5-95, Class A and Class B MIL-G-23827 Nomenclature Rivet. Universal H ead H I-Lok H i-Lok H i-Lok Hi-Lok Lock bolt Collar Collar Colla r Primer Sealant Grease 1 inch long by 1 . 751nch diameter rod , 2024-T4 or 

### 6061-T4 aluminum . See Figu re 2 .

727-52-0142 10

### BOEING SERVICE BULLETIN 727-52.0142

B. Parts N ecessary to Change Spares None C . Special Tools and Equipment The specia l tool shown In Figure 

### 2 of thi s bulletin c:an be made by the operator. Ma in tenance and overhaul tools c:an be necessary 

### as given I n any manua l s that are listed In Paragraph 

### 1 . 1., References , of th is bulletin . Operators should review their tool inven tory to make sure that tools are availabl e.

Jul26/90 

### REV 2 · Apr 15/93 727-52-0142 11

### BOEING SERVICE BULLETIN 727-52-0142

D . Existing Parts Ac countabil i ty The parts shown below are cha nged by th is service bulletin . The Quantity Is th e number of parts changed on each airplane . The Quantity of the indented part is the number of parts used on the next hig her assembly. Inst alled Part Number Nomenclature 65- 25339-5 Latch Cam Assemb l y Of: Sta . 600 

### + 4 .65 (Spares only) 69-21971 ·4 Latch Cam 69-23438-1 Latch Cam 69-21969·3. 

### -8, or -502 Bellcrank Assembly 65-25339-6 La tch Cam Assemb l y Of : Sta . 571.80 (Spares on l y) 69-23439-3 La tch Cam 69-23439-4 Latch Cam 69-21969-1, -7 , or Bellcrank Assembly -501 65-25339-7 La tch Cam Assembly Of : Sta. 528.20 (Spares only) 69- 23439-3 Latch Cam 69-23439-4 Latch Cam 69- 21969-2 , - 7, or Be ll crank Assembl y

-501 65-25339-8 Latch Cam Assembly Of : Sta . 495 .35 (Spares only) 69-21971-3 Latch Cam 69-23438-2 Latch Ca m 69-21969-4, -8, or Bellcrank Assembly -502 65-26120-1, -3, Hinge, Pressure Valve or-5 65-26120-2,-4, or Hinge, Pressure Valve -6 69-21971-3 or -501 Latch Cam 69-21971-4 or -502 Latch Cam 69-23439-1 or ·3 Latch Cam 69-23439-2 or -4 Latch Cam

Ju l 26/90 REV. 2 : Apr 15/93 Qty DC New Part Number 1 DIS 65-93535-13 1 DIS 65-93535-22 1 DIS 65· 93535-23 1 DIS 65· 93535-15 1 DIS 65-93535-12 1 DIS 65-93535-20 1 DIS 65-93535-17 1 DIS 65-93535-18 1 DIS 65-93535-11 1 DIS 65-93535-20 1 DIS 65-93535-17 1 DIS 65-93535-18 1 DI S 65-93535-10 1 DIS 65-93535-14 1 DIS 65-93535-16 1 DIS 65-93535-15 2 DIS 65-93535-7 2 DIS 65-93535-8 1 DIS 65-93535-14 1 DIS 65-93535-22 1 DIS 65-93535-20 1 DIS 65-93535-17 PNC 

# s s s s s s s s s s s s s s s s s s s s s s RC A A A A A A A A A A A A A A A A A A A A A A

727- 52-0142 

### 12

### BOEING S ERVICE BULLETIN 72 7-52 -0142
DC Disposition Code DIS Discard lhe part . PNC Part Number Code S This i s lhe new equlva l enl or repl acemen l part numbe r. RC Repl acemenl Code A Replacemenl nol perm llted: Do no l repl ace 

### a new part wllh an exisling part.



### Jul26 /90 REV. 2 : 

### Apr 15/93 

### 727-52-0142 13

### Jul26/90 REV . 2 : Apr 15/93 

### BOEING SERVICE BU L LETIN 727-52-0142

BLANK PAGE

727-52-0142 

### 14

### BOEING S ERV I CE BULLETIN 727- 52-0142

Ill. A CCO M PLISH M E NT I NSTRUCTI O NS NOTES : 1. The paragraphs Identified with letters give the general wor1< Instructions and the necessary tests. The Instructions i dentified with numbers on the figures give the recommended sequence of steps . 2. U n l ess specified differently, these d ime nsions and tolerances are used :

- A ll linear di m ensions a re i n i nches

- Tole rance on linear dimensions other than rive t and boll edge margin Is plus or minus 0 .03 Inch

- Ang ul ar tole rance is plus o r minus 2 degrees

- The hole dimensions for standard solid rive t s are found I n 727 Structu ral Repair Manua l Chapte r 51

- The torque lim it s to t ighten nu t s and bolls are found in 727 Struct ura l Repair Manual Chap te r 51. 3. Refer to 727 Structura l Repair M anual Chapter 51 for a lt ernative fasteners. 

### 4 . Obey all warnings and cautions In the specified manual sections. PART I - INSPECTION A. Do an lnspecllon of the hinge fittings and the l atch cams on the main cargo door as shown In Flgure 1 . 

### 8 . If any or the four hinge fittings ara wom beyond the limit given In Flgure 1, I ns tall new h i nge fitti ngs and l atch cams In the main cargo door as specified In PART II - R E PLACEMEN T, below . C. 

### If any of the four latch cams are wom or damaged as shown In Figure 1, Install new h i nge fittings and l atch cams I n the main cargo door as specified In PAR T II - REPLAC EMENT , below. P AR T II -RE PLAC E M E NT A. Make the h inge fitting tools for the pressure relief doors as shown in Figure 2. 

### 8 . Remove the interior lining and the i nsulation from the l ower area or the main cargo door (Reference - 727 Maintenance Manual, Subjects 52-34-161 and 52-34-171). C. Put a wor1< pl atform next to the airpl ane at the main cargo door. D. Partially open the main cargo door. Use wood blocks to support the door In the partially opened position as shown In the 727 Maintenance Manual , Subject 52-34-0, I nspection/Check. Cycle the latch cams Into the locked position with the door In the ope n position as shown In the 727 Maintenance Manua l Subject 52-34-0 . E . Remove pressure from the hydraulic system for the main ca rgo door (Reference - 727 M ain tenance Manual , Subject 52-11-0, Main tenance Practices) . F. Remove the most forward and aft main cargo door latch actuators as shOwn in the 727 Main tenance Manual , Subject 52-11-11 . 

### G. Remove the web and access cover from each pressure rallef door location as shown In Figure 

### 4 . H. Remove the pressure ralief doors and carefully drill out the rivets that attach the hinge fittings to the pressure relief doors as shown In Figu re 

### 5 , circle notes 

### 1 through 

### 9 . I. Remove the latch cams and the bellcranks from the main cargo door, and install new latch cams and bellcranks as shown In Figure 3 .

Jul26190 REV. 2 : Apr 15/93 727-52-01 42 15

### BOEIN G SERVI CE BULLETIN 727-52-0 142

J . lnslallthe pressure relief door and locate lhe new hinge fillings on the pressure relief doors as shown in Figure 5 , circle notes 10 through 26. K . I nstall the most forwar d and aft main cargo door latch actuators as shown In the 727 Maintenance Manua l Subject 52-11-11 . L. Operate the main cargo door as necessary to remove air f rom the hydraulic system for the main cargo door. Se l ect door ope n control and open door sufficient to remove the wood b lock s. Do not operate the main cargo door into the complete l y closed position while this step is done. M. Adjust the main cargo door as necessary and do a test o f the ma i n ca rgo door to make sure that II operates correcUy (Reference- 727 Maintenance Man u al, Subject 52-34-0, AdlustmenVTest). NOTE: I nspect to make sure that the tab on the marking bracket Is inserted in to the Index hole in the cam . Also do a check to see if the m arki ng bracket is visibl e through the viewport in the ca rgo door skin when the door is closed a n d the latch ca ms are In the l atched position . N . Do a lest of the warning system for the main cargo door to make sure thai 

### II ope rates correcUy (Reference- 727 Main tena n ce Manual, S u bject 52-70-00 or -01) 

### 0 . Do a test of the control system of the main cargo door to make sure that It operates correcUy. 

### P. I nstall the web and access cover at each pressure relief door location as shown in Figure 

### 6 . Q . I nstall the insulation and the interior li ning on the lower area of the ma i n ca rgo door (Reference - 727 Maintenance Manua l , Subjects 52-34-171 and 52-34-161) . R . Restore airplane to serviceable condition .

Jul26/90 REV . 2 : Apr 15193 727-52-0142 16

### BOE I NG SERVICE BULLETIN 727-52-0142
Illustration Table of Contents Tille Page Figure 1 . Inspection . . ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . • . . • . . . • . . . 18 F

igu re 2. Align men t Tool Fa b ricati on . . . . • . . . . . . . . . . . . . . . . . . . • . . . . . . . . • . . . . . . . . 20 Figu re 

### 3. Latch Cam Replacement . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . • . . . . . . . . . . . 21 Rgu re 4 . 

### Web Remova l . . . . . . . . . • . • . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . • . . • . . . . . 27 Fi g ure 5 . Hinge Fitting Repl acement. . .. . . • . . • . . .. . .. • .. . . . . . . .. .. . . . . . . . . . . .. 

### 28 Fi gure 

### 6 . Web Installation . . . . . . . . . . . . • . . . . . . . . • . . . . . . . . . . • . . . . . • . . . • . . . . . . . 32

Jul26/90 727-52-0142 REV. 2 : 

### Apr 15193 17

## ALMOS T THE SAME AS DETAIL I



# <

**'**

**~A** 

### HING E FITTING

Jul26190 REV 2: Apr 15/93 

### BOEING SERVICE BULLETIN 727-52-0142



## SEE DETAIL I

AS DETAIL

CF VD



# ~I NBD

PRESSURE RELIEF DOOR

TIP 

## OF HINGE 

### 2 FITTING 

# - 

# -- --.....___

# __



# /

- 0.12 

## INCH MAXIMUII FLAT AllOWED FIGURE 1 INSPECTION 

## VIEW A -A <2 PLACES)

727-52-0142 

### 18

### BOEING SERVICE BULLETIN 727-52-0142

() F II O 

# DETAIL I 

# ' LATCH 

## C

AM

The Instruction numbers shown below agree With the numbers shown Inside the circle symbols In the figure :

1 Do a visual Inspection or the area on each latch cam tha t contacts a hinge fitting on a pressure re l ief door 

### (4 places). 

### II the cam is notched 

## as shown, or lithe cam shows any damage beyond 0 .05 1nches deep from contact with the hinge fitting , replace the latch cams and the hmge fittings . 2 Measure the tip or each hinge fitting as shown (4 places) . 

### II any ol the hinge fittings are worn beyond the limit shown, replace the latch cams and the hinge fittings as shown In this service bullet in . Reier to the 727 Maintenance Manual , Subject 52-34-0 . NOTE : Removal ol the pressure relief door from the mai n cargo door may be necessary to do the inspection given In Step 2 , above lnstructJons for removal ol the pressure relief door are given i n 

### the 

### 727 Maintenance Manual , Subject 52-34-11 

### 3 II either 

### the 

### cam or the h1nge liWng Is 

### worn. measure 

### the overlap as shown in 

### View 

### AA Make sure that there i s m1ni mum of 0 . 15 i nch overlap 

### II there is less than a 0 . 15 1 nch overlap, replace the cam and the hinge fittings as shown 

### m this service bullebn .
Jul26190 REV, 

### 2 : Apr 

### 15/93 FIGURE 1 . I NSPECTION 727-52-0142 

### 1 9

### A 

# L 0 . 54 R 0 . 55 BOEING SERVICE BULLETIN 727-52-0142

# )~ 0. 84 R 

# ' / 0.86 A 

# _j 

# 1 0. 50 B 

# L 1. 0S OIA 1 . 10 •



### B 

# _j



# I 0.50 

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# ____J _L VIEW A-A VIEW B-B

The instruction number shown bel ow agree with the number shown inside the ci rcl e symbol in the figure.

1 Make the two alignment tools to the dimensions shown from one or the materials given below:

- 2024-T42 aluminum rod, 

### 1 . 751nch outside diameter

- 6061-T42 aluminum rod, 

### 1 . 75 inch outside diameter. FIGURE 2 . ALIGNMENT TOOL FABRICAT ION Ju l 26/90 REV. 2: Apr 15193 727-52-0142 

## 20

## c: 

# E

Jul26/90 

## SEE / DETAIL I DETAIL II

REV . 2 : Apr 15/93 

### BOEING SERVICE BULLETIN 727-52-0 1 42



## SE E DETAIL VI 

## SEE DETAIL V 

# e!> F W

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# ~INBD

F I GURE 3 . LATCH CAM REPLACEMENT 

### Ill

### C ARG O DOOR

I II

727-52-0142 21

### Jul26/90 REV. 2: Apr 

### 15/93 

### BOEING SERVICE BULLET I N 727·52-0142



## CF WO 

## DETAIL I AFT LAT CH CAMANO BELLCRANK ASSEMBLY SHOWN, FOR W ARD LATCH AND BELLCRANK ASSEM BLY OPPOSITE

SHEAR VEB 69-24209-() ..... ' 

# '-· I ', 

# _,_

DETAIL II VIEW LOO KING FORWARD c:::> 

## INBD AFT LUG ASSEMBLY SHOWN, FOR WARD LUG ASSEMBLY OPPOSITE FIGURE 3. LATCH CAM REPLACEMENT 

### 727·52·0 142 22

### BOEING SERVICE BULLETIN 727-52-0142



### 6 69 - 34974-3 

# (! A

Jul26/90 REV. 2 : Apr 

### 15/93 

### 7 6



## DETAIL Ill

, 6 5-93535 -1 9 [3; 69- 34974-4 6 

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### ACTU ATOR 

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## w o DETAIL IV FIG U RE 3. LATCH CAM REPLACEMENT 

### 727-52-0142 23

### Jul26190 REV. 2: Apr 15/93 

### BOEING SERVICE BULLETIN 727-52-0142

FIGURE3· LATCHCAM REPLACEMENT 72

### 7-52-0142 24

### BOEING S ERVIC E BUL L ETIN 727-52-0 142



## VIEWPORT DOOR SKIN -. 

# - c) I NB D 

# VIE W A -A 

# _,. ! K ARKING BRACKET

LATCH CA K

The instructions give n below appl y to lalch cams and bell cranks located at Body Stallons 

### 495, 530, 570. and 

### 610. See Details I , 11 . Il l , and V I for complete figures that show replacement of the forward and aft latch cam and bellcrank assembly. See details IV and V for complete figures that show replacement of the latch cam and bellcrank assembly located at Body Station 

### 530 and 

### 570. The Instructions given below agree with the numbers shown inside the circle symbols In the figure: 1 Fo r the most forward and aft latch cam, tnm 

### the shear web 

### 69-24209-( ' ) and extend the cut out of the lower beam web and doubler 

### 65-25338-( • ) Inboard, up to the maximum amount as shown . 

### Do not trim shear web or extend 

### the cut out of the lower beam web beyond what Is necessary for the removal of the lug assembly. Maintain 

### 0 .50 R or larger comer radius . On 

### the aluminum shear web 

### 69-24209-3, -4 and the lower beam web and doubler 

### 65-25338-( • ) , finish lrinvned areas with brushed on chemical film treatment 

### (Nodine or lridite), and one coat of BMS 

### 10-11 Type I primer Touch up w.th one coat of deoorabve enamel. On steel shear web 

### 69-24109-7 and 

### -8, finish trimmed areas w.th brush cadmium plate and one coal of BMS 

### 10-11 Type I pnmer Touch up with one coat of decorative enamel . 

### 2 Remove the fasteners that attach the Lug Assembly 

### 9-66095-1 and 

### -2 lo lhe frame . 3 Remove the special bolt that attaches tho latch actuator to the bellcrank . Keep the special bolt and hardware for later use. NOTE : 

### If the special bolt i s worn. corroded , or is missing finish . use a new Boll 

### 66-17789-1 . 4 Remove and discard lhe fasteners that auach lhe bellcrank to lhe latch cams 5 Remove lhe bellcrank and 

### the latch cams from lhe door, and dJscard 

### the bellcrank and the latch cams.



### Jul26/90 REV 2 : Apr 

### 15193 FIGURE 3. LATCH CAM REPLACEMENT 

### 727-52-0142 

### 25

### BOEING SERVICE BU LLETIN 727-52-0142

6 Use a screw NAS602-7 , two washers AN960PD8L and a nut NAS679A08W to I nstall the marking bracket on the new latch cam . Make sure that the tab on the marking bracket fils into the index hole on the cam . Make sure that the marking bracket Is visibl e through the viewport in the cargo door skin when the door is closed and the latch cams are in the latched position. CAUTION : Make su re that the correct marking bracket is I nstalled on each cam as shown I n Figure 3 . There are two different part numbered marking brackets. 

### If the wrong bracket is Installed on the cam, it will not be 

### visib l e through the viewport In the cargo door skin when the door Is In the latched pos ition, 7 Apply a th in coat of grease MI L-G-23827 (or equivalent) to the bearing surfaces of the new latch cams and the new bellcrank. 8 Apply primer (Refe rence - BMS 10-11, Type 

### I) to the tapered end of bellcrank . Do not allow the primer to dry 

### before the next step Is done . 9 Use the fasteners indicated to Install the new latch cams and the new bell crank In position on the cargo door. NOTE : Make sure that the forward and 

### all lug assembly are in place prior to installing the most forward and aft latch cams and bellcrank. 10 Attach the latch actuator to the new bellcrank . Use the special boll and hardware that was kept when the instructions given In Step 

### 3, above, were done . Torque the bolt with 50 to 80 Inch -pounds. 11 Install the Lug Assemb l y to the web . (Refer to 727 Structural Repair Manual 51-30-05) . The Instructions given below agree with the letter shown in the upper -l eft comer of the fas tener symbols in the figu re . A nu m ber In the lower-right comer or the fas tener symbol is the l ength or the fastener. A Insta ll a bolt NAS 1 1 04-20W with a washer BACW1 OP208S under the bollhead . Use a nut NAS679A4W to secure the boll . and torque the nut with 50 t o 80 Inch-pounds . B I ns tall a boll NAS1105-20W with a washer AN960C616L under the bolthead . Use a nut NAS679A5 to secure the boll , and torque the nut with 100 to 150 inch-pounds. C Install a countersink bolt BACB30EL5CN19 with a nut NAS679A5 . Torque the nut with 60 t o 65 inch-pounds. D Install BACB30GYBA( )X 

### Lockbolt with a BACC30K8 Collar .

F IGURE 3 . LATCH CAM REPLACEMENT Jut261 90 REV. 2: Apr 15/93 727-52-0142 26

### BOEING SERVICE BULLETIN 727-52-0142

e>F WD



# ~INBD The lnstruct1on numbers shown below agree with the numbers shown InSide the circle symbols In the figure .

1 Remove and keep the screws that attach the access panel for lhe pressure relief door, and remove and keep the access panel for later use 

### 2 Drill out or otherwise remove all fas teners that attach th e web to lhe structu re around the p ressure relief door. 

### 3 Remove and keep the web for later use



### FIGURE 4 WEB REMOVAL Jul26190 

### REV 2 Apr 15/93 727-52-0142 27Jul26/90 

## SEE DETAIL I FOR DOOR EXTERN AL**VIE W~** 



## STA 480

REV . 2 : Apr 15/93 

### BOEING SERVICE BULLETIN 727-52-0142



## O FWD

# ~INBD SEE DETAIL II STA 600D



# ______ I 

# 00000

=

# L~~**u** 

# --- ..j- ' DETAIL I 

## DOOR EXTERNAL VIEW A

### ~

FIGURE 5 . HINGE FITTING REPLACEMENT 

### 727-52-0142 28

### NUT 

### 7 1 13 

# -- 18 123

Jul26/90 

### BOEING SERVICE BULLETI N 727-52-0142



### 5

) 24 6 

# J)i9• ,!YE@_ PRESSURE R ELIEF DOOR 

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## BOLT 8ELLC RANK



## SECTION A - A

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### 1 6 1 21

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### ..,.. 1

_ 2 19 ALIGN"ENT 

## TOOLS

FIGURE 5 . HINGE F ITIING REPLACEMENT REV. 2 . Apr 15/93 

### 727-52·0142 29

### BOEING SERVICE BULLETIN 72 7-52-0 1 42

The Instruction numbers shown below agree with the numbers shown I nside the circle symbols in the figure . 1 Make sure thai the pressure relief door is closed and seated against Its cutout In the main cargo door. 

### 2 Make marks on the ou t s i de of the pressu re relief door and on the outside of t he cargo door skin with a marke r that wi ll not damage the pressure relief door o r the cargo doo r skin. Make sure that the marks on t he p ressure relief door are a ligned with the marks on t he cargo door sk i n. These marks will be used l ater to correcUy position the pressure relief door on the cargo door when the new hinge fittings are install ed as described i n Step 1 6, bel ow. 

### 3 A t the aft pressu re reli ef d oor l ocation only, remove the hydraulic tubes that are located Inboard of the pre ssure relief door. Te m po rarll y p l ug o r cap the open hydraulic t ubes to make sure that hydraulic fluid does not spill i n the pressure reli ef d oo r area in the ca rgo door. 

### 4 Remove the nu t , the bolt , the was hers and the spacers from the be ll crank on the torque tube that is above the pressure relie f door. Keep a ll of this hardwa re for later use. 

### 5 Remove t he nu t , the washer, and the bolt from the bellcrank on the torque tube that Is above the pressure relie f door. Keep all o r this hardwa re for later use. 

### 6 Rotate the bell crank on the torque lube so that it Is out of the way oft he pressure relief door . 

### 7 Remove the nut, the special bol t, the washers, and the spacer from the hinge poin t s of the pressure relief doo r. Keep all of this ha rdware for later use. 

### 8 Remove the pressu re relief door f rom the ca rgo door. 9 Ca refully drill out the rivets tha i attach the hinge fittings to the pressure re li ef door. Discard the o l d hinge fittings . 

### 10 Pu t t he pressure relief door Into the cargo door and align the marks on the pressure relief door with the marks on the ca rgo door skin. 

### 1 1 Wed ge the pressure relief door so that it is firm l y seated in its cu tout on the cargo door. N OTE : M ake su re that the outside surface of the pressure door Is flush with the ou tside skin or the main cargo door. Refer to the 

### 727 Maintenance M anual, Subject 

### 52-34-1 1 . 12 Put the alignmen t tool s that were made In Figure 

### 2 inside the cup of the cam as shown. 13 Attach the new hinge fittings 65-93535-7 (art) and 65-93535-8 (forward) to the pivot points wi th the hardware that was kept when Step 7, above, was done . Make sure that all of the hardware is installed exactly like It was before it was removed . 

### 14 Make sure that the new hinge fittings tum freely on the special bolt, and that the mating surfaces of the hinge fittings and the pressure relief door are in contact with each other.

Jul26/90 REV . 

### 2 : Apr 15/93 FIGURE 

### 5 . HINGE FITTING REPLACEMENT 

### 727-52-0142 30

# I BOEING SERVICE BULLETIN 727 -52-0142

15 Rotate the h1nge fittings until the bp touches the alignment tool as shown . 

### t!Q!S; Make sure that there 

### Js no Interference between the cam and the hinge fitt1ng . If the hinge fitting Interferes with the cam . then do the steps that follow: 

## a. Trim up t o a maximum of 0 .05 Inch from the ou tboard surface on the hinge fi tting . Make sure that the removal of malarial Is done so to main lain the radius of the part . Maintain a 

### 63 AA surface finish or better. 

### b. Fi nish filed a rea wi th two coats of B MS 10-1 1 Type I pri mer. c. Con la ct Boeing If a trim of 0.05 does not stop the Interference . 16 Tlghtly clamp the hinge fittings to the pressu re relief door and remove the wedges that held the pressure relief door In position In the cargo door. 17 Make sure that the pressure relief 

### door moves freely with 

### the new hinge fiwngs 18 Remove the nut. 

### the special bolt. the washers , and the spacer 

### from the hinge poonts of the pressure relief door. Keep all of this hardware for later use. 

### 19 Remove the pressure relief door from the cargo door. and remove the alignment tools from cup of the cam . Make su re that the new hinge fittings are not moved out of the clamped position when the pressure relief door Is removed . 20 Carefu ll y drill match i ng 0 .257 Inch diame ter (drill Size "F") 

### holes In the new hinge fitti ngs at locations where fastener h oles exist In the pressure reli ef door. Use of a dri ll bushing t o make 1/8 Inch diameter pilo t holes In the new hinge fittings Is recommended, foll owed by gradual enlargement of the fastener holes to the final size . NOTE : As an option, the operator may use HI·Loks BACB30FP8A( ) and collars BACC30 M81n place of rivets to inslall the hi nge fitti ng to the pressure door. To use HI·Loks Carefully dnll matching 0.266 to 0.270 Inch diameter holes In the new hinge fittings at the locations where fasteners holes exi st in the pressure rel1ef 

### door. 21 Remove the new h1nge fittings from the pressure relief door and deburr all fastener holes I n the hinge fittings . 22 Use rivets MS204 7088-14 or optional fasteners coated With sealant (Reference • BMS 5-95, Class A) to l nslall the new hinge fittings on the pressure relief door. 23 Put the pressure relief door I n position In lhe cargo door and attach lhe hi nge filbngs to the pivot points with the hardware that was kept when Step 18, above. was done. Make sure that a ll of the hardware Is Installed exactly like It was before 

### It was removed, and make sure that the pressure relief door moves freely on Its hinges. Torque the nut with 50 to 80 Inch-pounds. 24 Rolate the bellcrank on the torque tube that Is above the pressure relief door I nto correct position on the torque tube and attach the bellcrank to the torque tube with the hardware that was kept when Step 5, above , was done . Torque the nul With 25 to 35 Inch-pounds. 25 Use the hardware that was kept when Step 4 . above , was done 

### to attach the bellcr a n k to the slotted bracket o n the pressure relief 

### door Torque the nut With 25 to 35 tnch-pounds 26 Install the two 

### hydrauf](; tubes that were removed when Step 3 . above , 

### was done FIGURE 5 . HINGE FITTING REPLACEMENT Jul26/90 REV 

### 2 · Apr 15/93 727-52-0142 31

### BOEING SERVICE BULLETIN 727 -52-0142

SE E DETA IL II

I 

### 3 

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Jul 26190 REV . 2 : Apr 15/93 

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# DET AI L 1 FIGURE 6 WEB INSTALLATION 

### 727 -52..{)142 32

### BOEING SERVICE BULLETIN 727 -52-0142 

# (})'1) 1\ 

# CD (1 4 PLACES) 

# T

# ~ \

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### .._ 

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The i nstructi on n u mbers shown be low ag ree wilh the numbers shown i ns ide t he circle sym bols I n the fi gu re .

1 C l ean all o l d se alan t f rom mating surfaces ofthe web and the ca rgo door stru cture. 2 Appl y sea l an t ( Refe rence - B M S 5-95, C l ass B) to mating s urfaces of web and ca rgo door structure. Do not a ll ow the sealant to 

### dry before the nex t s tep is done . 3 Use t he fasteners listed bel ow at each p ressure re li ef door location to Insta ll the webs tha t were kept when t he instructions In Agure 3 were done. 4 Use the screws that were kep t when Agure 3 was done to Install the access cover on the web . The i nstruc«ons g i ven below agree with the tetter shown in the upper-left comer of the fastener symbols in the figure . A number in the lower-right corner oft he fas tener symbol is the length of the fastener. A Drill fastener holes In web and ca rgo door s tructure to 0. 200 (+ 0 .003 or - 0.000) Inch diameter. Insta ll a 

### Hi-Lok BACB30FP6·() wllh a collar BACC30M6 . 

### 8 I nstall a rivet M S20470D6-7 (24 P l aces).



### FIGURE 6 . WEB INSTALLATION Jul26/90 REV . 2: Apr 15/93 727-52-0142 

### 33

## IIDIIND

Number: 727-52-0142 Date: July 26, 1990 Revision 2: April15 , 1993 ATA System : 5234 Prepared By: Mark Miller 

### Commercial Airplane Group 

# 727 Service Bu ll etin Evalu a tion Form

SUBJECT: DOORS- MAIN CARGO DOOR- LATC H CAM REPLACEMENT AND PRESSURE RELIEF DOOR H INGE FITTIN G REPLACEMENT Use this evaluation form to tell us wha t you th in k of the quality of this service bu ll etin. We will use the data that you give us to improve the quality of our service bulletlns. Please Incl ude data about these or other i tems:

- Did this service bu ll etin mee t your estimate of quality?

- How easy is this service bulletin to understand?

- Are the Planning Information, Material Information and Accomplishment Instructions satisf actory?



### - Wilt you do t his service bulletin fu ll y? If not, please tell us why.

- Is the Manpower estima te satisfactory? NOTE : P l ease do not use this evaluation form to tell us to make changes to your manuals. To make these changes , pl ease use e Publication Change Request (PCR) form . Please give us this data : OPERATOR : PREPARED BY: ORGANIZATION : TE LEPHONE NUMBER: COMMENTS: TODAY'$ DATE : ------- T ITLE: TELEX CODE :

If you have other comments please use the other side. Thank you for the time you used to complete this form . G i ve the completed eva luation form to your Boeing F ield Service Representative or send the eva l uation form directly to this address: R.G. Kelsey, Manager Service Bulletin Engineering Boeing Commercial Airplane Group P .O. Box 3707, Mall Stop 2L-02 SeatUe, WA 98124-2207

BOEING COMMERC.Al NRPL.AIIIE GROUP P .O . BOX 3707 SEATTLE. WASHINGTON 981244 2207